US7923671B1 - Drive device for projectile fins - Google Patents
Drive device for projectile fins Download PDFInfo
- Publication number
- US7923671B1 US7923671B1 US11/528,377 US52837706A US7923671B1 US 7923671 B1 US7923671 B1 US 7923671B1 US 52837706 A US52837706 A US 52837706A US 7923671 B1 US7923671 B1 US 7923671B1
- Authority
- US
- United States
- Prior art keywords
- fin
- motors
- projectile
- fins
- drive device
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related, expires
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/60—Steering arrangements
- F42B10/62—Steering by movement of flight surfaces
- F42B10/64—Steering by movement of flight surfaces of fins
Definitions
- the technical scope of the present invention is that of devices to control projectile fins, that is devices which, by the action of a motor, enable deployed fins to be pivoted.
- Fins act as stabilizers for a projectile but may also play a role in piloting, similar to the elevons or ailerons of an aircraft, controlled in rotation by a motor piloted by an electronic system.
- the piloting of the projectile enables its trajectory to be corrected in flight to rectify any launching errors or to orient it towards a target after said target's detection.
- Such fins suffer from the principal drawback of needing to be of a large size if they are to be effective (the length of the fin is usually around one caliber), which makes it impossible for the projectile to be fired from a cannon of the same caliber.
- the projectile fitted with such a mechanism may be a missile, a rocket, or sub-projectile.
- French patents FR-2864613 and FR-2846079 describe devices to deploy projectile fins and lock them in their deployed position.
- French Patent FR-2846080 describes a device to deploy and pilot projectile fins.
- the device disclosed in that document enables the simultaneous orientation of pairs of fins integral with a common control shaft.
- the main advantage of this device lies in its use of only two motors to orient the four fins.
- the aim of the present invention is to supply a drive device for deployable fins of a projectile, such device being compact and able to withstand the accelerations experienced during firing of a projectile.
- the invention thus relates to a device to drive in rotation fins of a projectile, the fins being of the deployable type integral with fin heads, such device incorporating motors and a body with respect to which said fin heads can be oriented along an axis of spin substantially orthogonal to the projectile's longitudinal (Z) axis, wherein the body incorporates a circular groove in which the fin heads are driven in rotation by the motors by means of substantially ring portion shaped sliders which slide in the circular groove.
- the sliders slide in a plane that is orthogonal to the longitudinal projectile axis.
- each slider incorporates a notch and an arm integral with the drive shaft of a motor cooperating with the notch to make the sliders slide in the groove.
- each slider incorporates a portion of a rack gear onto which meshes a pinion gear integral with the drive shaft of a motor.
- each slider incorporates a hole cooperating with a finger integral with a fin head to make it pivot.
- the end of the finger cooperating with the slider is in the form of a spherical head.
- the drive motors for the fins are positioned with their axes of rotation substantially parallel to the longitudinal projectile axis.
- the motors are evenly spaced angularly around the longitudinal projectile axis.
- the motors are positioned angularly in pairs, one motor of each pair on each side of each of opposing fins.
- the motors are positioned in pairs in an angular quadrant between two fins.
- a first advantage of the device according to the invention lies in the fact that it effectively withstands the accelerations due to the projectile being fired.
- Another advantage of the device lies in the fact that it enables different configurations of the angular positioning of the fin drive motors.
- Another advantage of the device lies in its compactness and in the manufacturing simplicity of its constituent parts.
- FIGS. 1 and 2 show a perspective view of a fin rotation drive device according to the invention
- FIG. 3 is a top view of a slider
- FIG. 4 is a section view of the fin rotation drive device along plane AA of FIG. 1 ;
- FIG. 5 shows the same device as shown in FIG. 1 , but whose fins are in different positions;
- FIGS. 6 and 7 show a top view of variant embodiments of the device according to the invention.
- FIG. 8 shows a variant embodiment of the slider and its drive means.
- FIG. 1 shows a perspective view of a projectile fin rotation drive device according to the invention.
- the fin drive device is here shown outside of a projectile body (not shown) and in a configuration in which the fins are deployed and substantially parallel to longitudinal axis Z of the projectile.
- FIG. 2 is the same view of the same embodiments of the invention as shown in FIG. 1 but wherein, for the purposes of improved comprehension of the invention, the body 4 has not been shown.
- the fin rotation drive device includes a body 4 , sliders 1 , motors 2 and fin heads 6 connected with fins 7 .
- the fin heads 6 may be oriented along an axis of spin (respectively, X and Y) orthogonal to longitudinal axis Z of the projectile.
- the motors 2 are evenly spaced angularly around longitudinal axis Z of the projectile and each includes a drive shaft 12 , with an axis of spin (Z 1 , Z 2 , Z 3 and Z 4 ) parallel to longitudinal axis Z of the projectile.
- the body 4 incorporates a circular groove 3 in which the sliders 1 are inserted and are able to slide following a circular trajectory around axis Z.
- the sliders 1 are substantially in the shape of a ring portion or sector and incorporate a hole 11 at one end (which can be seen in FIG. 3 ) and a notch 9 at the other end.
- Each fin head 6 is connected to a slider 1 by a finger 5 connected with the fin head 6 and cooperating with the hole 11 in the slider 1 .
- Each motor 2 is connected to a slider 1 by an arm 8 , connected with the drive shaft 12 of the motor and cooperating with the notch 9 in the slider 1 .
- FIG. 3 is a top view of a slide.
- the slider is substantially in the shape of a ring sector or portion.
- the notch 9 has a first portion 13 that is substantially oblong and radial with respect to the curvature of the slider and a second outwardly opening portion 17 delimited by two oblique planes 14 opposite one another.
- the notch 9 is symmetrical with respect to a radial axis of the slider and ends with a cylindrical portion 13 a .
- the oblong portion 13 of the notch is also delimited by two parallel planes 13 b .
- the arm 8 cooperating with the notch 9 incorporates a first part 15 connected with the drive shaft 12 of the motor, a central part 16 whose edges are intended to cooperate with the oblique planes 14 of notch 9 , and a substantially spherical or cylindrical end 10 , of a diameter substantially less than or equal to the width of the oblong portion 13 of the notch.
- Portion 17 is shaped to ensure disengagement to leave the arm 8 sufficient angular clearance.
- Portion 13 ensures guidance with minimal play of the end 10 of the arm.
- the hole 11 is an oblong hole, arranged substantially radially with respect to the curvature of the slider 1 .
- the finger 5 cooperating with the hole 11 includes a spherical head of a diameter substantially less than the width of the oblong hole 11 .
- FIG. 4 is a section view of the fin rotation drive device along the plane AA shown in FIG. 1 .
- This Figure clearly shows that the sliders 1 are placed at the bottom of the groove 3 in the body 4 .
- each slider 1 incorporates an oblong hole 11 with which the upper part 20 of the finger 5 cooperates.
- the bottom of the groove 3 incorporates drill holes or slots 19 (only one of which can be seen) providing a passage for each finger 5 .
- the fin heads 6 include a housing 18 in which the lower part 21 of the finger 5 is tightly housed (the lower part 21 of the finger may, for example, be screwed into the housing 18 ).
- the fin heads 6 are held in the body 4 by a pivot type link (not shown) with an X axis substantially orthogonal to longitudinal axis Z of the projectile.
- the device according to the invention operates as follows:
- the fins 7 are deployed and each is connected with the fin head 6 .
- the systems to deploy and secure fin with their heads are sufficiently known to those in this art and thus do not require further description. Reference may be made, however, to French patent FR-2846079 describing such a device which incorporates a spring to ensure the swiveling of the fin 7 with respect to its head 6 .
- two opposing motors perform a rotation of their drive shafts 12 along their axes Z 1 and Z 3 (and/or Z 2 and Z 4 ) in opposing directions.
- the rotation of each shaft 12 causes its slider 1 to slide in the groove 3 by means of the arm 8 , whose end 10 presses on the first portion 13 of the notch 9 .
- the opposite pairs of sliders move in the opposite directions about the longitudinal axis Z of the projectile, causing the movement of the upper part 20 of the fingers 5 of the opposite fin heads 6 .
- the slot 19 at the bottom of the groove will be large enough to enable the displacement of the finger 5 when this is driven by the slider 1 .
- the finger 5 is connected with the fin head 6 .
- the notch 11 drives the upper end 20 of the finger 5 thereby causing the fin head 6 to swivel.
- the fin heads 6 are thus driven in rotation around their spin axis X (or Y) to orient the fins 7 .
- the oblique planes 14 of the notch 9 constitute limit stops limiting the rotation of the fins. Indeed, when one edge of the central part 16 of the arm 8 presses on an oblique plane 14 of the notch, the arm 8 is no longer able to drive the slider 1 and the fin 7 is in its position of maximum orientation.
- FIG. 5 shows the device according to the invention in the configuration where the fins 7 are no longer parallel to longitudinal axis Z of the projectile, but oriented to modify the projectile's trajectory.
- the motors 2 have moved the sliders 1 in opposing directions F 1 and F 2 .
- the sliders acting on the opposing fins have been moved in opposing directions to keep the opposite fins in the same plane.
- the circular groove 3 is in a plane that is orthogonal to longitudinal axis Z of the projectile and the slides sliders 1 therefore slide in a plane orthogonal to longitudinal axis Z of the projectile.
- Such an arrangement has the advantage of being particularly able to withstand a projectile's accelerations along this longitudinal axis Z, namely when it is being fired.
- they may be positioned with their axes of rotation substantially in parallel to longitudinal axis Z of the projectile.
- the upper end 20 of the finger 5 will preferentially be made in the form of a spherical head to facilitate its cooperation with the oblong hole 11 .
- the device according to the invention is simple in design. It is particularly easy to machine a single groove in the body 4 . This groove provides guidance for the four sliders and ensures the symmetry of the movements.
- the length of the sliders 1 can be varied without necessarily modifying the operation of the device and the extent of the invention.
- Such a variant embodiment of the invention will advantageously enable a fin rotation drive device to be produced whose angular positioning of the motors 2 is uneven.
- FIG. 6 schematically shows a top view of an embodiment of the invention in which the motors are arranged in pairs.
- the fin drive device incorporates two short sliders 1 a and 1 d and two long sliders 1 b and 1 c , respectively arranged in opposition with respect to the projectile's longitudinal axis Z.
- Motors 2 a to 2 d are arranged in pairs on either side of the opposing fins 7 .
- Such an embodiment of the invention advantageously enables the motors 2 to be integrated in an uneven more compact manner, whilst retaining the device's ability to withstand accelerations.
- the invention may also be made using sliders which each have a different length, thereby advantageously enabling a non-symmetrical spacing of the motors 2 and easy adaptation to the constraints of integrating motors and electronics into a projectile body.
- the deployment and control of the fins may thus be symmetrical with motorization arranged in a non-symmetrical manner.
- FIG. 7 schematically shows a top view of another embodiment of the invention in which the motors are arranged in pairs.
- motors 2 a to 2 d are arranged in pairs 2 a - 2 b and 2 c - 2 d in angular quadrants 24 a and 24 b between two fins 7 .
- Such an arrangement advantageously enables a large amount of space to be freed which may then be used, for example, to integrate the onboard electronics or power sources.
- This embodiment advantageously implements sliders 1 of identical length.
- FIG. 8 shows a variant embodiment of the slider and its drive means.
- the notch 9 and arm 8 have been removed.
- Each slider 1 incorporates a portion of rack 23 onto which meshes a pinion 22 integral with the drive shaft 12 of a motor 2 (not shown).
- the rack 23 may advantageously and easily be made by machining the slider 1 . Rotating the pinion 22 thus causes the slider 1 to slide.
Landscapes
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Toys (AREA)
- Control Of Electric Motors In General (AREA)
- Control Of Multiple Motors (AREA)
- Elimination Of Static Electricity (AREA)
- Stroboscope Apparatuses (AREA)
- Bakery Products And Manufacturing Methods Therefor (AREA)
- Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
- Fittings On The Vehicle Exterior For Carrying Loads, And Devices For Holding Or Mounting Articles (AREA)
- Catching Or Destruction (AREA)
- Transition And Organic Metals Composition Catalysts For Addition Polymerization (AREA)
Abstract
Description
Claims (9)
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0510164A FR2891618B1 (en) | 2005-10-05 | 2005-10-05 | DEVICE FOR DRIVING PROJECTILE GOVERNMENTS. |
FR0510164 | 2005-10-05 | ||
FR05.10164 | 2005-10-05 |
Related Child Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US12/510,150 Continuation US20100203498A1 (en) | 2003-08-22 | 2009-07-27 | Methods and compositions for identifying anti-hcv agents |
Publications (2)
Publication Number | Publication Date |
---|---|
US20110073705A1 US20110073705A1 (en) | 2011-03-31 |
US7923671B1 true US7923671B1 (en) | 2011-04-12 |
Family
ID=36551894
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US11/528,377 Expired - Fee Related US7923671B1 (en) | 2005-10-05 | 2006-09-28 | Drive device for projectile fins |
Country Status (7)
Country | Link |
---|---|
US (1) | US7923671B1 (en) |
EP (1) | EP1772698B1 (en) |
AT (1) | ATE475060T1 (en) |
DE (1) | DE602006015582D1 (en) |
ES (1) | ES2349303T3 (en) |
FR (1) | FR2891618B1 (en) |
IL (1) | IL178325A (en) |
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20110180655A1 (en) * | 2010-01-28 | 2011-07-28 | Nexter Munitions | Device for simultaneous deployment of the control surfaces of a projectile |
US20140061365A1 (en) * | 2012-08-31 | 2014-03-06 | Nexter Munitions | Projectile with steerable fins and control method of the fins of such a projectile |
US8921749B1 (en) * | 2013-07-10 | 2014-12-30 | The United States Of America As Represented By The Secretary Of The Navy | Perpendicular drive mechanism for a missile control actuation system |
US9285196B2 (en) * | 2011-05-13 | 2016-03-15 | Gordon Harris | Ground-projectile guidance system |
US10280786B2 (en) | 2015-10-08 | 2019-05-07 | Leigh Aerosystems Corporation | Ground-projectile system |
US20220178665A1 (en) * | 2020-12-04 | 2022-06-09 | Bae Systems Information And Electronic Systems Integration Inc. | Control plate-based control actuation system |
US11371814B2 (en) | 2015-08-24 | 2022-06-28 | Leigh Aerosystems Corporation | Ground-projectile guidance system |
Families Citing this family (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8026465B1 (en) * | 2009-05-20 | 2011-09-27 | The United States Of America As Represented By The Secretary Of The Navy | Guided fuse with variable incidence panels |
FR2949848B1 (en) | 2009-09-10 | 2012-09-28 | Nexter Munitions | DEVICE FOR OPENING AND LOCKING A DUCK FIN. |
IL207800B (en) * | 2010-08-25 | 2018-12-31 | Bae Systems Rokar Int Ltd | Control apparatus for guiding a cannon shell in flight and method of using same |
US8624172B2 (en) * | 2010-10-13 | 2014-01-07 | Woodward Hrt, Inc. | Shift lock assembly |
US20160187111A1 (en) * | 2014-08-10 | 2016-06-30 | Jahangir S Rastegar | Methods and Devices For Guidance and Control of High-Spin Stabilized Rounds |
DE102015005135A1 (en) * | 2015-04-22 | 2016-10-27 | Diehl Bgt Defence Gmbh & Co. Kg | Missile rudder system |
KR101903254B1 (en) * | 2016-12-28 | 2018-10-01 | 주식회사 한화 | Apparatus for controlling roll and pitch canard of precision guidance kit |
FR3078152B1 (en) * | 2018-02-22 | 2021-11-05 | Nexter Munitions | ORIENTABLE GOVERNANCE PROJECTILE |
FR3080912B1 (en) | 2018-05-02 | 2020-04-03 | Nexter Munitions | PROJECTILE POWERED BY STATOREACTOR |
US11892275B2 (en) * | 2022-05-25 | 2024-02-06 | Raytheon Company | Drive mechanism for control surface actuation |
Citations (17)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4709877A (en) * | 1983-11-25 | 1987-12-01 | British Aerospace Plc | Deployment and actuation mechanisms |
US5048772A (en) | 1990-01-26 | 1991-09-17 | Thomson-Brandt Armements | Device for roll attitude control of a fin-stabilized projectile |
US5505408A (en) * | 1993-10-19 | 1996-04-09 | Versatron Corporation | Differential yoke-aerofin thrust vector control system |
US5806791A (en) * | 1995-05-26 | 1998-09-15 | Raytheon Company | Missile jet vane control system and method |
US5823469A (en) * | 1994-10-27 | 1998-10-20 | Thomson-Csf | Missile launching and orientation system |
US6073880A (en) * | 1998-05-18 | 2000-06-13 | Versatron, Inc. | Integrated missile fin deployment system |
US6186443B1 (en) * | 1998-06-25 | 2001-02-13 | International Dynamics Corporation | Airborne vehicle having deployable wing and control surface |
US6247666B1 (en) * | 1998-07-06 | 2001-06-19 | Lockheed Martin Corporation | Method and apparatus for non-propulsive fin control in an air or sea vehicle using planar actuation |
US6325325B1 (en) * | 1999-04-16 | 2001-12-04 | Giat Industries | Device for translational braking of a projectile on its trajectory |
WO2002018867A1 (en) | 2000-08-31 | 2002-03-07 | Bofors Defence Ab | Canard fin unit |
GB2374055A (en) | 2000-10-07 | 2002-10-09 | Bayern Chemie Gmbh Flugchemie | Rudder blade linkage arrangement for missile guidance |
US6637699B2 (en) * | 2002-03-25 | 2003-10-28 | Lockheed Martin Corporation | Method and apparatus for controlling a trajectory of a projectile |
US6827310B1 (en) * | 2003-09-22 | 2004-12-07 | The United States Of America As Represented By The Secretary Of The Navy | Apparatus and method for fin actuation in a portable missile |
US7175131B2 (en) * | 2003-12-31 | 2007-02-13 | Giat Industries | Deployment and drive device for projectile control surfaces |
US7219579B2 (en) * | 2004-03-10 | 2007-05-22 | Lockheed Martin Corporation | Apparatus and method for actuating control surfaces |
US7246539B2 (en) * | 2005-01-12 | 2007-07-24 | Lockheed Martin Corporation | Apparatus for actuating a control surface |
US20080029641A1 (en) * | 2005-02-07 | 2008-02-07 | Bae Systems Information And Electronic Systems | Three Axis Aerodynamic Control of Guided Munitions |
Family Cites Families (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2846080B1 (en) | 2002-10-17 | 2007-05-25 | Giat Ind Sa | DEVICE FOR DEPLOYING AND TRAINING PROJECTILE GOVERNMENTS |
FR2846079B1 (en) | 2002-10-17 | 2006-08-18 | Giat Ind Sa | DEVICE FOR LOCKING / UNLOCKING AND DRIVING PROJECTILE GOVERNMENTS |
-
2005
- 2005-10-05 FR FR0510164A patent/FR2891618B1/en not_active Expired - Fee Related
-
2006
- 2006-09-27 EP EP06291517A patent/EP1772698B1/en active Active
- 2006-09-27 IL IL178325A patent/IL178325A/en active IP Right Grant
- 2006-09-27 DE DE602006015582T patent/DE602006015582D1/en active Active
- 2006-09-27 ES ES06291517T patent/ES2349303T3/en active Active
- 2006-09-27 AT AT06291517T patent/ATE475060T1/en not_active IP Right Cessation
- 2006-09-28 US US11/528,377 patent/US7923671B1/en not_active Expired - Fee Related
Patent Citations (18)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4709877A (en) * | 1983-11-25 | 1987-12-01 | British Aerospace Plc | Deployment and actuation mechanisms |
US5048772A (en) | 1990-01-26 | 1991-09-17 | Thomson-Brandt Armements | Device for roll attitude control of a fin-stabilized projectile |
US5505408A (en) * | 1993-10-19 | 1996-04-09 | Versatron Corporation | Differential yoke-aerofin thrust vector control system |
US5630564A (en) * | 1993-10-19 | 1997-05-20 | Versatron Corporation | Differential yoke-aerofin thrust vector control system |
US5823469A (en) * | 1994-10-27 | 1998-10-20 | Thomson-Csf | Missile launching and orientation system |
US5806791A (en) * | 1995-05-26 | 1998-09-15 | Raytheon Company | Missile jet vane control system and method |
US6073880A (en) * | 1998-05-18 | 2000-06-13 | Versatron, Inc. | Integrated missile fin deployment system |
US6186443B1 (en) * | 1998-06-25 | 2001-02-13 | International Dynamics Corporation | Airborne vehicle having deployable wing and control surface |
US6247666B1 (en) * | 1998-07-06 | 2001-06-19 | Lockheed Martin Corporation | Method and apparatus for non-propulsive fin control in an air or sea vehicle using planar actuation |
US6325325B1 (en) * | 1999-04-16 | 2001-12-04 | Giat Industries | Device for translational braking of a projectile on its trajectory |
WO2002018867A1 (en) | 2000-08-31 | 2002-03-07 | Bofors Defence Ab | Canard fin unit |
GB2374055A (en) | 2000-10-07 | 2002-10-09 | Bayern Chemie Gmbh Flugchemie | Rudder blade linkage arrangement for missile guidance |
US6637699B2 (en) * | 2002-03-25 | 2003-10-28 | Lockheed Martin Corporation | Method and apparatus for controlling a trajectory of a projectile |
US6827310B1 (en) * | 2003-09-22 | 2004-12-07 | The United States Of America As Represented By The Secretary Of The Navy | Apparatus and method for fin actuation in a portable missile |
US7175131B2 (en) * | 2003-12-31 | 2007-02-13 | Giat Industries | Deployment and drive device for projectile control surfaces |
US7219579B2 (en) * | 2004-03-10 | 2007-05-22 | Lockheed Martin Corporation | Apparatus and method for actuating control surfaces |
US7246539B2 (en) * | 2005-01-12 | 2007-07-24 | Lockheed Martin Corporation | Apparatus for actuating a control surface |
US20080029641A1 (en) * | 2005-02-07 | 2008-02-07 | Bae Systems Information And Electronic Systems | Three Axis Aerodynamic Control of Guided Munitions |
Cited By (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20110180655A1 (en) * | 2010-01-28 | 2011-07-28 | Nexter Munitions | Device for simultaneous deployment of the control surfaces of a projectile |
US8592737B2 (en) * | 2010-01-28 | 2013-11-26 | Nexter Munitions | Device for simultaneous deployment of the control surfaces of a projectile |
US9285196B2 (en) * | 2011-05-13 | 2016-03-15 | Gordon Harris | Ground-projectile guidance system |
US9546854B2 (en) | 2011-05-13 | 2017-01-17 | Gordon L. Harris | Ground-projectile guidance system |
US10295320B2 (en) | 2011-05-13 | 2019-05-21 | Gordon L. Harris | Ground-projectile guidance system |
US20140061365A1 (en) * | 2012-08-31 | 2014-03-06 | Nexter Munitions | Projectile with steerable fins and control method of the fins of such a projectile |
US9297622B2 (en) * | 2012-08-31 | 2016-03-29 | Nexter Munitions | Projectile with steerable fins and control method of the fins of such a projectile |
US8921749B1 (en) * | 2013-07-10 | 2014-12-30 | The United States Of America As Represented By The Secretary Of The Navy | Perpendicular drive mechanism for a missile control actuation system |
US11371814B2 (en) | 2015-08-24 | 2022-06-28 | Leigh Aerosystems Corporation | Ground-projectile guidance system |
US10280786B2 (en) | 2015-10-08 | 2019-05-07 | Leigh Aerosystems Corporation | Ground-projectile system |
US20220178665A1 (en) * | 2020-12-04 | 2022-06-09 | Bae Systems Information And Electronic Systems Integration Inc. | Control plate-based control actuation system |
US11650033B2 (en) * | 2020-12-04 | 2023-05-16 | Bae Systems Information And Electronic Systems Integration Inc. | Control plate-based control actuation system |
Also Published As
Publication number | Publication date |
---|---|
EP1772698B1 (en) | 2010-07-21 |
US20110073705A1 (en) | 2011-03-31 |
DE602006015582D1 (en) | 2010-09-02 |
ES2349303T3 (en) | 2010-12-29 |
IL178325A0 (en) | 2007-02-11 |
EP1772698A1 (en) | 2007-04-11 |
FR2891618B1 (en) | 2010-06-11 |
FR2891618A1 (en) | 2007-04-06 |
ATE475060T1 (en) | 2010-08-15 |
IL178325A (en) | 2012-12-31 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US7923671B1 (en) | Drive device for projectile fins | |
US20050151000A1 (en) | Deployment and drive device for projectile control surfaces | |
US5108051A (en) | Deployment mechanism of a projectile fin | |
US4869442A (en) | Self-deploying airfoil | |
US9546854B2 (en) | Ground-projectile guidance system | |
US6073880A (en) | Integrated missile fin deployment system | |
ES2239157T3 (en) | FINING UNIT. | |
EP2100090B1 (en) | Spin stabilizer projectile trajectory control | |
US8426788B2 (en) | Guidance control for spinning or rolling projectile | |
US8674278B2 (en) | Control of projectiles or the like | |
US8592737B2 (en) | Device for simultaneous deployment of the control surfaces of a projectile | |
US10458764B2 (en) | Canard stowage lock | |
US8894003B2 (en) | Air vehicle and method for operating an air vehicle | |
WO2007133247A2 (en) | Fin retention and deployment mechanism | |
US5480111A (en) | Missile with deployable control fins | |
EP2276998B1 (en) | Apparatus for air brake retention and deployment | |
EP2268996B1 (en) | Methods and apparatus for guidance of ordnance delivery device | |
US9163915B2 (en) | Projectile with steerable control surfaces and control method of the control surfaces of such a projectile | |
ES2547455T3 (en) | Projectile with adjustable rudders and control procedure for the rudders of said projectile | |
US11015909B2 (en) | Projectile with steerable control surfaces | |
US7100865B2 (en) | Method and apparatus for stowing and deploying control surfaces of a guided air vehicle | |
RU2085825C1 (en) | Rocket with normal aerodynamic configuration | |
JPS58205100A (en) | Projectile |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
AS | Assignment |
Owner name: THE BOARD OF TRUSTEES OF THE LELAND STANFORD JUNIO Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:GLENN, JEFFREY S.;EINAV, SHIRIT;ELAZAR, MENASHE;REEL/FRAME:017014/0594 Effective date: 20051020 |
|
AS | Assignment |
Owner name: GIAT INDUSTRIES, FRANCE Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:HUGUENIN, SIMON;ROY, RICHARD;REEL/FRAME:018457/0010 Effective date: 20060915 |
|
AS | Assignment |
Owner name: NEXTER MUNITIONS, FRANCE Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:GIAT INDUSTRIES;REEL/FRAME:022714/0883 Effective date: 20090131 |
|
STCF | Information on status: patent grant |
Free format text: PATENTED CASE |
|
FPAY | Fee payment |
Year of fee payment: 4 |
|
MAFP | Maintenance fee payment |
Free format text: PAYMENT OF MAINTENANCE FEE, 8TH YEAR, LARGE ENTITY (ORIGINAL EVENT CODE: M1552); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY Year of fee payment: 8 |
|
FEPP | Fee payment procedure |
Free format text: MAINTENANCE FEE REMINDER MAILED (ORIGINAL EVENT CODE: REM.); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY |
|
LAPS | Lapse for failure to pay maintenance fees |
Free format text: PATENT EXPIRED FOR FAILURE TO PAY MAINTENANCE FEES (ORIGINAL EVENT CODE: EXP.); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY |
|
STCH | Information on status: patent discontinuation |
Free format text: PATENT EXPIRED DUE TO NONPAYMENT OF MAINTENANCE FEES UNDER 37 CFR 1.362 |
|
FP | Lapsed due to failure to pay maintenance fee |
Effective date: 20230412 |